Nomen est omen. [http://en.wikipedia.org/wiki/Salami Salami] rocket is about building a [http://en.wikipedia.org/wiki/Hybrid_rocket hybrid rocket] with a gaseous [http://en.wikipedia.org/wiki/Oxidizing_agent oxydizer] (N<sub>2</sub>0) and salami as propellants.

Nomen est omen. [http://en.wikipedia.org/wiki/Salami Salami] rocket is about building a [http://en.wikipedia.org/wiki/Hybrid_rocket hybrid rocket] with a gaseous [http://en.wikipedia.org/wiki/Oxidizing_agent oxydizer] (N<sub>2</sub>0) and salami as propellants.

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Zeile 7:

Zeile 10:

= Oxydizer =

= Oxydizer =

I chose [http://en.wikipedia.org/wiki/N2O N<sub>2</sub>O] over [http://en.wikipedia.org/wiki/Oxygen O<sub>2</sub>] because although N<sub>2</sub>O carries a lot of conjectural inert nitrogen (64%) oxygen is much harder to handle (tank filling, storage & injection). Additionally the [http://en.wikipedia.org/wiki/Nitrogen nitrogen], though not participating in combustion, raises the fuel erosion rate and cooles the nozzle enough to reuse it many times.

I chose [http://en.wikipedia.org/wiki/N2O N<sub>2</sub>O] over [http://en.wikipedia.org/wiki/Oxygen O<sub>2</sub>] because although N<sub>2</sub>O carries a lot of conjectural inert nitrogen (64%) oxygen is much harder to handle (tank filling, storage & injection). Additionally the [http://en.wikipedia.org/wiki/Nitrogen nitrogen], though not participating in combustion, raises the fuel erosion rate and cooles the nozzle enough to reuse it many times.

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Since the alternatives i found are quite expensive, i use the nitrous oxyde of [http://en.wikipedia.org/wiki/Whipped-cream_charger whipped-cream chargers]. By the way, never search for [http://www.google.at/search?q=sahnespender&ie=utf-8&oe=utf-8&aq=t&rls=com.ubuntu:en-US:unofficial&client=firefox-a "Sahnespender"] at google.

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Since the alternatives i found are quite expensive, i use the nitrous oxyde of [http://en.wikipedia.org/wiki/Whipped-cream_charger whipped-cream chargers].

= Fuel =

= Fuel =

Zeile 17:

Zeile 20:

= Parts =

= Parts =

[[Bild:Scaled-dscn9121.jpg|thumb|Overview of the rocket parts]]

[[Bild:Scaled-dscn9121.jpg|thumb|Overview of the rocket parts]]

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All parts directly participating in the combustion would have to sustain at least 51 bar (vapor pressure of N<sub>2</sub>0 at 20°C) but for reasons of safety i assume 200bar as the minimum.

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All parts directly participating in the combustion would have to sustain at least 51 bar<br>(vapor pressure of N<sub>2</sub>0 at 20°C) but for reasons of safety i assume 200bar as the minimum.

* [http://en.wikipedia.org/wiki/Pressure_vessel Run Tank]: A light-weight container for the oxydizer capable of sustaining enough pressure

* [http://en.wikipedia.org/wiki/Pressure_vessel Run Tank]: A light-weight container for the oxydizer capable of sustaining enough pressure

Zeile 27:

Zeile 30:

* Body tube: Enhances airodynamic properties of the rocket and encapsulates the motor.

* Body tube: Enhances airodynamic properties of the rocket and encapsulates the motor.

After a few backyard tests with a rather improvised device, we tested the actual motor at [http://metalab.at/wiki/Stadtflucht2 Lindabrunn]. Special thanks to [[User:Kyrah|kyrah]] and [[User:MariusKintel|marius]] for support, pyromantic inspiration and fuel sponsoring.

After a few backyard tests with a rather improvised device, we tested the actual motor at [http://metalab.at/wiki/Stadtflucht2 Lindabrunn]. Special thanks to [[User:Kyrah|kyrah]] and [[User:MariusKintel|marius]] for support, pyromantic inspiration and fuel sponsoring.

WTF?

Oxydizer

I chose N2O over O2 because although N2O carries a lot of conjectural inert nitrogen (64%) oxygen is much harder to handle (tank filling, storage & injection). Additionally the nitrogen, though not participating in combustion, raises the fuel erosion rate and cooles the nozzle enough to reuse it many times.
Since the alternatives i found are quite expensive, i use the nitrous oxyde of whipped-cream chargers.

Fuel

Salami: High efficency hydrocarbon based fuel ;)

Simulation

Im using RockSim to simulate the flight stability of the rocket. The behaviour of the N20/ hybrid motor is simulated by an external model programmed in C++.

Parts

Overview of the rocket parts

All parts directly participating in the combustion would have to sustain at least 51 bar(vapor pressure of N20 at 20°C) but for reasons of safety i assume 200bar as the minimum.

Run Tank: A light-weight container for the oxydizer capable of sustaining enough pressure

Throttle Valve: A valve to allow precise regulation of the oxydizer flow from the run tank to the combustion chamber.